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    SUCTION SIDE TURBINE BLADE TIP COOLING
    1.
    发明申请
    SUCTION SIDE TURBINE BLADE TIP COOLING 审中-公开
    抽吸侧涡轮叶片冷却

    公开(公告)号：WO2014058493A3

    公开(公告)日：2014-06-19

    申请号：PCT/US2013050429

    申请日：2013-07-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHLUS WIESLAW A ,  THOMEN SETH J

    IPC: F01D5/18 ,  F02C7/12

    CPC classification number: F01D5/20 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供在径向方向上延伸的翼型件。 翼型件具有设置在压力和吸力壁之间的冷却通道，其朝向翼型件的尖端延伸。 尖端包括分隔压力和吸力壁的口袋。 围绕的冷却孔将冷却通道流体地连接到口袋。 所述被切割的冷却孔包括凹入到所述吸入壁的表面并暴露于所述口袋的部分。

    2.
    发明专利
    未知

    公开(公告)号：FR2649180B1

    公开(公告)日：1992-12-31

    申请号：FR9008291

    申请日：1990-06-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GUDRIDGE JOAN M ,  SENATRO CLEMENT A ,  CHLUS WIESLAW A

    IPC: F02C9/28 ,  F16L3/12 ,  F16L3/137 ,  F16L3/123 ,  H02G3/26

    Abstract: A support structure 10 for positioning a conduit 12 for various environments including that of an aircraft gas turbine engine is disclosed. Various construction details are developed for the support structure which facilitate assembly of portions of the support structure. The support structure includes a clamp assembly 18 and a clip 22 for orienting the clamp assembly in the proper direction. Orientation of the clamp assembly is facilitated by features of the clip. These features include a pair of tabs 32, 34 which face each other from either side of the clamp assembly. In one detailed embodiment, the clamp includes a laterally extending tab 92 to block the channel formed between the pair of longitudinally extending tabs.

    CABLE CLAMP ALIGNMENT DEVICE
    3.
    发明专利
    CABLE CLAMP ALIGNMENT DEVICE 未知

    公开(公告)号：GB2235491A

    公开(公告)日：1991-03-06

    申请号：GB9014082

    申请日：1990-06-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GUDRIDGE JOAN M ,  SENATRO CLEMENT A ,  CHLUS WIESLAW A

    IPC: F02C9/28 ,  F16L3/12 ,  F16L3/137

    Abstract: A support structure 10 for positioning a conduit 12 for various environments including that of an aircraft gas turbine engine is disclosed. Various construction details are developed for the support structure which facilitate assembly of portions of the support structure. The support structure includes a clamp assembly 18 and a clip 22 for orienting the clamp assembly in the proper direction. Orientation of the clamp assembly is facilitated by features of the clip. These features include a pair of tabs 32, 34 which face each other from either side of the clamp assembly. In one detailed embodiment, the clamp includes a laterally extending tab 92 to block the channel formed between the pair of longitudinally extending tabs.

    4.
    发明专利
    未知

    公开(公告)号：DE602004019872D1

    公开(公告)日：2009-04-23

    申请号：DE602004019872

    申请日：2004-12-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHEROLIS ANTHONY ,  CHLUS WIESLAW A

    IPC: F01D5/14

    Abstract: A turbine blade (20) has an undercut (33) beneath its platform (26) at a trailing edge (24). The undercut (33) has a complex shape to move thermal stress concentration away from the platform. A preferred undercut shape has a pair of curved fillets (32,36) at upper and lower extents of the undercut (33) with an intermediate straight section (34). The intermediate straight section is preferably parallel to a principle stress field of the platform (26).

    5.
    发明专利
    未知

    公开(公告)号：FR2649180A1

    公开(公告)日：1991-01-04

    申请号：FR9008291

    申请日：1990-06-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GUDRIDGE JOAN M ,  SENATRO CLEMENT A ,  CHLUS WIESLAW A

    IPC: F02C9/28 ,  F16L3/12 ,  F16L3/137

    Abstract: A support structure 10 for positioning a conduit 12 for various environments including that of an aircraft gas turbine engine is disclosed. Various construction details are developed for the support structure which facilitate assembly of portions of the support structure. The support structure includes a clamp assembly 18 and a clip 22 for orienting the clamp assembly in the proper direction. Orientation of the clamp assembly is facilitated by features of the clip. These features include a pair of tabs 32, 34 which face each other from either side of the clamp assembly. In one detailed embodiment, the clamp includes a laterally extending tab 92 to block the channel formed between the pair of longitudinally extending tabs.

    STRUCTURE FOR POSITIONING A CONDUIT
    7.
    发明专利
    STRUCTURE FOR POSITIONING A CONDUIT 未知

    公开(公告)号：GB2235491B

    公开(公告)日：1993-04-14

    申请号：GB9014082

    申请日：1990-06-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GUDRIDGE JOAN M ,  SENATRO CLEMENT A ,  CHLUS WIESLAW A

    IPC: F02C9/28 ,  F16L3/12 ,  F16L3/137

    Abstract: A support structure 10 for positioning a conduit 12 for various environments including that of an aircraft gas turbine engine is disclosed. Various construction details are developed for the support structure which facilitate assembly of portions of the support structure. The support structure includes a clamp assembly 18 and a clip 22 for orienting the clamp assembly in the proper direction. Orientation of the clamp assembly is facilitated by features of the clip. These features include a pair of tabs 32, 34 which face each other from either side of the clamp assembly. In one detailed embodiment, the clamp includes a laterally extending tab 92 to block the channel formed between the pair of longitudinally extending tabs.

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